Propellers TRIZ Cases

Reducing blade setting angles eliminates flow separation, lowering noise while maintaining wind pressure.

Refractory oxide platelets and glass-forming binders prevent oxygen ingress and accommodate thermal expansion at temperatures above 3000 degrees F.

A static conduit within a power drive shaft houses hydraulic rotating couplings to transfer fluid power across the gear assembly interface.

I-shaped hub arms with elastomeric bearings support rotor blades, resolving the trade-off between high-speed coaxial operation and blade pitch adjustment.

Merged hub assembly reduces axial and radial dimensions by integrating hydraulic actuation with direct electrical power supply to variable pitch blades.

Motor-driven pump supplies lubricant pressure to windmilling turbomachines.

Carbon foam spar core matches structural layer thermal expansion to prevent cracking and improve bond strength.

Embedded EFPI sensors detect residual stress and microstrain within propeller blade composite structures, enabling real-time structural integrity assessment.

Reversing rotor thrust enables recovery from accidental collisions, ensuring safe indoor surveillance operations.

Modifying airfoil leading edge radius increases negative stall angle of attack.

A resilient baffle deflects to provide tool access for nosecone bolt maintenance.

Aft cambered helicopter rotor blades delay stall at high Mach numbers by maintaining attached flow and reducing drag.

A centrifugal compressor impeller uses optimized blade angle distribution to increase shroud side relative velocity.

Dynamic blade tip geometry minimizes induced drag and turbulence by optimizing aerodynamic performance across varying flight conditions.

Ball screw release mechanism decouples blades from counterweights during governor failure, preventing catastrophic blade release.

Inner platform interference fit eliminates the separate inner ring, reducing material costs and total pressure loads while maintaining rigidity.

A cylindrical fluid distributor transfers hydraulic pressure from fixed inlets to rotating actuator chambers within a turboprop engine.

A fan blade with a wing part and flap part forming a predetermined angle enhances airflow efficiency.

Oil-immersed actuator prevents grease migration seizure and dissipates heat during extended helicopter rotor blade pitch adjustments.

A composite propeller spar uses a closed root section with collet retention to secure the blade without fasteners.

A retractable flight rotor system uses a spiral spline and groove mechanism to linearly move blades along the shaft for deployment or retraction.

Guide rails constrain structural hoop movement to prevent interference with the duct center body while enabling ±25 degree vane rotation for mode conversion.

Optimizing backward and forward inclining angles on impeller vanes improves discharge pressure while keeping energy consumption low.

A turbine bucket assembly uses a ligament with bore holes to connect platform and lower body cooling circuits.

Segmented ceiling mount structure employs arc slots and adjustable gaskets to resolve structural stability versus ease of alignment trade-offs.

Angled blower blades rotate to optimize airflow, increasing suction pressure to transport difficult particulate materials further without hose blocking.

Flow-driven acoustic resonators near blade tips modify propeller sound fields by directing energy to cancel tonal noise in specific directions.

Inverting drain location to the root area allows larger bores that prevent obstruction and eliminate noise while draining condensation.

Aircraft fuel supply apparatus switches between fuselage and wing tanks using multiple pump units to manage fluid flow.

Segmented torque pin assemblies adjust gas turbine blade ring vertical spacing via variable thickness shims, eliminating costly machining time.

Curved blade root hooks distribute centrifugal loads across optimized contact surfaces to minimize local stress concentrations.

An aft plate with apertures regulates cooling gas flow to suppress hot gas ingress and prevent premature blade fatigue.

Segmented leading and trailing edges on VTOL propellers reduce noise propagation and centrifugal hub stress.

A buckling component prevents the position-limiting part from leaving, ensuring secure fixation and preventing blade loosening.

A rotating blade features an optimized airfoil section and a cover forming a radial seal to manage steam flow.

Radial passageways feed an outer plenum to cool the tip shroud, reducing creep and leakage without adding weight.

A fan blade tip recess alters passage area to attenuate unsteady pressure waves, reducing divergent vibration at high altitudes.

Composite fan blades use oppositely inclined fibers to generate shear forces that resist untwisting during high-speed rotation.

Positioning the connector at 70 to 90 percent of blade radius minimizes turbulent flow and maintains static pressure in low air flow zones.

A harmonic drive reduction gear system transmits rotational motion to adjust variable pitch propeller rotor blades.

Segmented erosion protection units shield rotor blades from particulate impacts, resolving the trade-off between wear resistance and blade flexibility.

Diffusion-based markers estimate turbo machinery temperatures without complex sensors, avoiding destructive testing.

A Ni-Fe forging superalloy with controlled Nb content enables precipitation of fine gamma-prime particles to enhance high-temperature strength.

Resistive heating of rotor disks mitigates thermal stress from uneven air flows during startup.

Merging the electric motor rotor with the turbine rotor eliminates gear reducers and separate mounting structures, reducing weight and complexity.

An impeller hub air exhausting structure directs hot motor air outward, preventing heat accumulation and contaminant ingress.

Embedding a composite insert in the foam core prevents shear-induced cracking and stabilizes the blade against bulging under flight loads.

A fan assembly uses frangible rotor blades and a pre-selected casing distance to increase initial resistance after bladeout.